Monolithic superstructure for load path optimization

ABSTRACT

The present disclosure generally relates to monolithic superstructures for supporting a rotating shaft coupled to a rotor relative to a stator. An integral superstructure supports the rotating component. The superstructure includes a bearing portion that contacts the shaft. A stator portion, is spaced a critical dimension radially outward, from the rotor. A first annular transfer portion extends axially forward from the bearing to the stator portion. A second annular transfer portion extends axially aft from the stator portion to a mounting flange. The mounting flange connects the superstructure to a frame. The superstructure maintains a critical dimension between the rotor and the stator as the temperature of the superstructure increases. The rotor may be a compressor impeller in a gas turbine engine and the stator may be an aero component that transfers air into a combustor.

INTRODUCTION

The present disclosure generally relates to monolithic superstructuresfor supporting a rotating shaft coupled to a rotor relative to a stator.In an example, the rotor is an impeller for a gas turbine engine and thestator is an aero component for directing compressed air from theimpeller.

BACKGROUND

In a gas turbine engine, intake air is compressed by a compressor. Fuelis added to the compressed air and ignited in a combustor. The expandinghot air passes through a turbine and out of a nozzle providing thrust.The turbine converts some of the energy of the expanding hot air intorotational energy for powering the compressor.

An interface between the compressor and combustor includes criticalspacing between the rotating impeller and a stationary aero component.In an aspect, the rotating impeller is a final centripetal compressorimpeller that produces highly compressed air. The stationary aerocomponent directs the compressed air into the combustor while diffusingthe pressure and reducing swirling currents within the compressed air.The alignment and clearance between the impeller and the aero componentis a critical dimension that affects the performance of the gas turbineengine. If the components become misaligned or the clearance becomes toogreat, the compressed air does not correctly enter the combustor.

In conventional gas turbine engines, an impeller shroud is mounted to acombustor case (e.g., via bolts or rivets). The aero component issupported at the connection between the impeller shroud and combustorcase. As temperatures of the engine increase, thermal expansion causesthe aero component to move with respect to the impeller. Accordingly,the alignment and clearance between the aero component and the impellerchanges, leading to decreased performance of the engine.

FIG. 1 is schematic diagram showing a cross-sectional view of anexemplary conventional system 100 including an interface 102 between acompressor 110 and combustor 120. A compressor case 112 is coupled withan impeller shroud 116. An impeller 114 rotates along with the shaft126. The impeller shroud 116 is coupled to a combustor case 122 via aconnector 118. The shaft 126 is rotatably supported by bearings 128. Thebearings 128 transfer load from the shaft 126 to a sump housing 134. Thesump housing 134 is coupled to the aero component 130, which in turn ismounted to the combustor case 122 at the connection between theconnector 118 and the combustor case 122. The combustor case 122includes a mounting point 124 for mounting the system 100 to a vehicleor other frame (e.g. a generator housing).

A load path 136 illustrates the distribution of load from the shaft 126in the conventional system 100. The load is applied to the bearings 128and transferred to the sump housing 134. The sump housing 134 transfersload to the aero component 130, which in turn transfers load to both thecompressor 110 via the connector 118 and to the combustor 120 includingthe mounting point 124.

The inset portion 150 illustrates relative movement of the impeller 116and the aero component 130 as the temperature of the system 100 changes.As indicated by the solid lines, when the system is relatively cold, theimpeller 116 and the aero component 130 are aligned with a smallclearance therebetween. The clearance may be, for example, approximately20 mils. As illustrated by the dashed lines, when the system isrelatively hot, thermal expansion causes the hot aero component to shiftradially outward and longitudinally distal. These directions are due, inpart, to the aero component 130 exerting load to the compressor 110 viathe connector 118, which adds a longitudinal component to the expansion.The hot impeller 152 shifts radially outward. The clearance between theimpeller 116 and the aero component 150 increases and the componentsbecome misaligned.

In view of the above, it can be appreciated that there are problems,shortcomings or disadvantages associated with supporting a rotor such asan impeller with respect to a stator such as an aero component in gasturbine engines, and that it would be desirable if improved systems andmethods for supporting a rotor with respect to a stator were devised.

SUMMARY

The following presents a simplified summary of one or more aspects ofthe invention in order to provide a basic understanding of such aspects.This summary is not an extensive overview of all contemplated aspects,and is intended to neither identify key or critical elements of allaspects nor delineate the scope of any or all aspects. Its purpose is topresent some concepts of one or more aspects in a simplified form as aprelude to the more detailed description that is presented later.

In one aspect, the disclosure provides an apparatus for transferringload from a rotating component including a longitudinal shaft and arotor. The apparatus includes an integral superstructure supporting therotating component. The integral superstructure includes a bearingportion that contacts the shaft. The integral superstructure includes astator portion, spaced a critical dimension radially outward, from therotor. The integral superstructure includes a first annular transferportion extending axially forward from the bearing to the statorportion. The integral superstructure includes a mounting flange thatconnects the superstructure to a frame. The integral superstructureincludes a second annular transfer portion extending axially aft fromthe stator portion to the mounting flange.

In another aspect, the disclosure provides a method of distributingbearing load. The method includes transferring a load from a rotatingshaft to a bearing portion of a superstructure via contact between theshaft and the bearing portion. The method includes transferring the loadfrom the bearing portion via a first annular support of thesuperstructure to a stator portion. The method includes transferring theload from the stator portion of the super structure to a second annularsupport. The method includes transferring the load from the secondannular support to a mounting tab. The method includes transferring theload from the mounting tab to a vehicle.

In another aspect, the disclosure provides a component of a gas turbineengine comprising. The component includes a monolithic superstructureincluding an outer case including a longitudinally proximal diffusercase portion, at least one mounting flange, and a longitudinally distalcombustor case portion. The monolithic superstructure also includes anaero component connected to the outer case via an annular aero portionsupport, the aero component including a diffuser portion and a deswirlerportion comprising a plurality of conjoined tubes extending from aradial end of the diffuser portion to an interior of the combustor caseportion.

In yet another aspect, the disclosure provides a method of supportingloads in a gas turbine engine. The method includes transferring a loadfrom a rotating shaft to a bearing portion of a sump housing via contactbetween the shaft and the bearing portion. The method includestransferring the load from the bearing portion via a conical member ofthe sump housing to an aero component including a diffuser portion and adeswirler portion comprising a plurality of conjoined tubes extendingfrom a radially distal end of the diffuser portion to an interior of acombustor case. The method includes transferring the load from the aerocomponent to an annular aero component support connected to theplurality of conjoined tubes. The method includes transferring the loadfrom the annular aero component support to a mounting tab. The methodincludes transferring the load from the mounting tab to a framesupporting the gas turbine engine.

These and other aspects of the invention will become more fullyunderstood upon a review of the detailed description, which follows.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is schematic diagram showing an example of a conventional gasturbine engine including an interface between a compressor and acombustor.

FIG. 2 illustrates a perspective view of an exemplary superstructureaccording to an aspect of the disclosure.

FIG. 3 illustrates a top view of the exemplary superstructure of FIG. 2.

FIG. 4 illustrates a forward view of the exemplary superstructure ofFIG. 2.

FIG. 5 illustrates an aft view of the exemplary superstructure of FIG.2.

FIG. 6 illustrates an axial cross section of the exemplarysuperstructure of FIG. 2.

FIG. 7 illustrates another axial cross section of the exemplarysuperstructure of FIG. 2.

FIG. 8 illustrates a radial cross-section through a forward region ofthe exemplary superstructure.

FIG. 9 illustrates another radial cross-section through an aerocomponent of the exemplary superstructure.

FIG. 10 is schematic diagram showing an example of a load path for theexemplary superstructure.

DETAILED DESCRIPTION

The detailed description set forth below in connection with the appendeddrawings is intended as a description of various configurations and isnot intended to represent the only configurations in which the conceptsdescribed herein may be practiced. The detailed description includesspecific details for the purpose of providing a thorough understandingof various concepts. However, it will be apparent to those skilled inthe art that these concepts may be practiced without these specificdetails. In some instances, well known components are shown in blockdiagram form in order to avoid obscuring such concepts.

As used herein, the terms “axial” or “axially” refer to a dimensionalong a longitudinal axis of an engine. The term “forward” used inconjunction with “axial” or “axially” refers to moving in a directiontoward the engine inlet, or a component being relatively closer to theengine inlet as compared to another component. The term “aft” used inconjunction with “axial” or “axially” refers to moving in a directiontoward the rear or outlet of the engine, or a component being relativelycloser to the outlet than the inlet.

As used herein, the terms “radial” or “radially” refer to a dimensionextending between a center longitudinal axis of the engine and an outerengine circumference. The use of the terms “proximal” or “proximally,”either by themselves or in conjunction with the terms “radial” or“radially,” refers to moving in a direction toward the centerlongitudinal axis, or a component being relatively closer to the centerlongitudinal axis as compared to another component. The use of the terms“distal” or “distally,” either by themselves or in conjunction with theterms “radial” or “radially,” refers to moving in a direction toward theouter engine circumference, or a component being relatively closer tothe outer engine circumference as compared to another component. As usedherein, the terms “lateral” or “laterally” refer to a dimension that isperpendicular to both the axial and radial dimensions.

FIGS. 2-9 illustrate an exemplary monolithic superstructure 200according to an aspect of the disclosure. FIG. 2 illustrates aperspective view of the monolithic superstructure 200. The monolithicsuperstructure 200 may be a superstructure for a combustor in a gasturbine engine. In an aspect, the monolithic superstructure 200 is be asingle integrated component that performs functions of multiplecomponents in conventional combustors. For example, the monolithicsuperstructure 200 perform functions of an aero component, whichtypically includes a separate diffuser, deswirler, swirl plate, anddiffuser case. The monolithic superstructure 200 also performs thefunctions of a combustor case assembly (e.g., routing fuel, air, andinstrumentation to various components of the combustor). The monolithicsuperstructure 200 also performs the functions of a bearing sump ofsupporting the shaft and managing turbine cooling air using an innershroud. As discussed in further detail below, by combining the variousfunctions of combustor components into an integrated component, themonolithic superstructure 200 reduces the total weight of the combustor.The monolithic superstructure 200 also allows for design of optimizedpaths, thereby requiring lower oil volumes and transport lengths.Further, the monolithic superstructure eliminates assembly risks andfastener failures.

The monolithic superstructure 200 generally includes an outer case 210that corresponds to a conventional combustor case and a diffuser case.As best seen in FIGS. 3 and 7, the outer case 210 may include a diffusercase portion 250 at a longitudinally proximal region and a combustorcase portion 260 at a longitudinally distal region. The outer case 210includes fuel nozzle ports 212 in the combustor case portion 260 forreceiving fuel lines and mounting fuel nozzles. The outer case 210 alsoincludes mounting tabs 214 located between the diffuser case portion 250and the combustor case portion 260. The mounting tabs 214 are spacedabout the outer case 210 and extend radially outward. The mounting tabs214 are used to mount the monolithic superstructure 200 to a frame suchas a vehicle frame or a generator frame. The diffuser case portion 250includes a compressor flange 252 for mounting to a compressor case. Theouter case 210 also includes igniter ports 216 for passing an ignitionwire through the outer case 210. The outer case 210 also includesinstrumentation ports 218 for passing instruments and or wires throughthe outer case 210. The outer case 210 also includes cooling airpassages 254 for routing cooling air from a forward portion of themonolithic superstructure 200 to an aft component such as a turbine.

As best seen in FIGS. 6 and 7, the monolithic superstructure 200 alsoincludes a centrally located bearing sump housing 230. The bearing sumphousing 230 includes bearing supports 232 for mounting bearings thatsupporting a shaft 234 (shown in FIG. 4). The bearing sump housing 230further includes a conical portion 236 that supports an aero component300. The conical portion 236 is an annular transfer portion extendinglongitudinally proximally from the bearing supports 232 toward the aerocomponent 300. The conical portion 236 transfers a load from the bearingsupports 232 to the aero component 300. In an aspect, the conicalportion 236 is shaped to maintain a position of the aero component 300with respect to the bearing sump housing 230 and an impeller. Thebearing sump housing 230 further includes a turbine cooling passage 240defined between the conical portion 236, the aero component 300, and aninner combustor shroud 148. The turbine cooling passage 240 draws cleanair from the aero component 300 and provides the clean air to turbinecooling blades (not shown) via an accelerator 242. The inner combustorshroud guides the clean air and also provides a heat shield for thebearing sump housing 230. The bearing sump housing further includes abearing sump sealing surface 244. For example, the bearing sump sealingsurface 244 may be an inwardly extending flange. The bearing sumpsealing surface 244 may form a seal for the bearings. The bearing sumphousing includes a turbine mounting surface 246 for connecting to aturbine.

The aero component 300 receives air from a compressor impeller 114 andprovides compressed air to the combustor. For example, the aerocomponent 300 performs functions traditionally performed by a diffuserand a deswirler. In an aspect, the compressor impeller 114 may beconsidered a rotor and the aero component 300 may be considered astator. The aero component 300 divides an interior of the outer case 210into a forward region and an aft region. As will be discussed in furtherdetail below, the aero component 300 is also a load bearing componentthat transfers loads from the bearing sump housing 230 to the outer case210 and the mounting tabs 214. The aero component 300 includes adiffuser portion 310, a back wall swirl plate 320, deswirler tubes 330,and an aero component support 370.

FIG. 8 illustrates a lateral cross-section along the line 8-8 in FIG. 3.The diffuser portion 310 is an annular member extending radially inwardto an edge 312. FIG. 9 illustrates a lateral cross-section along theline 9-9 in FIG. 3 through the diffuser portion 310. As best seen inFIG. 9, the diffuser portion 310 includes a plurality of internalpassages 314 extending radially outward from the edge 312. The openingsof the passages at the edge 312 are aligned with the final compressorimpeller. The internal passages 314 expand in diameter as they extendfrom the edge 312 toward the deswirler tubes 330. As discussed infurther detail below, the clearance between the diffuser portion 310 andthe compressor impeller may be a performance critical spacing. Forexample, as the distance between the diffuser portion 310 and theimpeller increases, pressurized air is less efficiently transferred tothe aero component 300 via the internal passages 314.

The back wall swirl plate 320 is a plate located aft of the compressorimpeller. The back wall swirl plate 320 deflects air exiting thecompressor impeller to a radially outward direction. In an embodiment,the back wall swirl plate 320 further includes an impeller backwallstiffener 322. The impeller backwall stiffener 322 is an annular memberwith a triangular cross section that resists forces from the impeller.Further, the impeller backwall stiffener 322 provides frequency tuningto cancel resonant frequency noise generated by the engine.

The deswirler tubes 330 are a plurality of conjoined tubes that extendfrom the diffuser portion 310 to the inside of the combustor caseportion 260. Each tube first extends radially outward from the diffuserportion 310. Each tube then curves both longitudinally and laterally. Inan aspect, the lateral curvature is opposite a direction of the impellermovement. Accordingly, the deswirler tubes 330 reduce lateral swirlingof the compressed air. The longitudinal curvature of the deswirler tubes330 extends from the forward region to deswirler outlets 334 locatedwithin the combustor case portion 260 in the aft region. The deswirlertubes 330 may be the only path from the forward region to the aftregion. In an aspect, the deswirler tubes 330 may include air extractionports 332 for turbine cooling and sump pressurization. For example, theair extraction ports may connect an interior of the deswirler tubes 330to the turbine cooling passage 240.

The aero component support 370 is an annular member that supports theaero component 300 with respect to the outer case 210. The aerocomponent support 370 transfers bearing loads from the aero component300 to the outer case 210 near the mounting tabs 214. The aero componentsupport 370 extends longitudinally and radially from the deswirler tubes330 to the outer case 210. In an aspect, the outer case 210 may be arelatively lower temperature than the aero component 300 and the bearingsump housing 230. For example, in operation, the aero component 300 maybe hotter than the outer case 210 by 200 degrees Fahrenheit or more. Thebearing sump housing 230 may be even hotter than the aero component 300.

Various properties of the aero component support 370 may be selected fora particular engine to optimize transfer of loads and thermalmanagement. In particular, the shape of the aero component support 370may be selected to maintain the position of the aero component 300 withrespect to the impeller as the temperature of the engine increases. Forexample, the aero component support 370 may allow radial expansion ofthe aero component 300, while resisting longitudinal movement of theaero component 300. The radial expansion of the aero component 300 maycorrespond to radial expansion of the impeller, thereby maintaining acritical clearance between the impeller and the aero component. Byresisting longitudinal movement of the aero component 300, the aerocomponent support 370 maintains an alignment between the impeller andthe diffuser portion 310.

FIG. 10 is a schematic diagram illustrating a load path 1136 for anexemplary superstructure. The shaft 126 exerts load on the bearingsupports 232. The bearing supports 232 transfer the load to the bearingsump housing 230. The conical portion 236 transfers the load to the aerocomponent 300. In this example, the conical portion is connected to theaero component between the back wall swirl plate 320 and the deswirlertubes 330. The deswirler tubes 330 transfer the load to the annular aerocomponent support 370. The annular aero component support 370 transfersthe load to the outer case 210 including the mounting tabs 214.

The diffuser portion 310 is positioned a critical dimension from theimpeller 114. The diffuser portion 310 is supported by the conicalportion 236 and by the annular aero component support 370 via thedeswirler tubes 330. It should be noted, that the diffuser portion 310is not directly connected to the diffuser case portion 250. Accordingly,the load path 1136 does not include an axial component through thediffuser portion 310, unlike the load path 136 in FIG. 1. The inset 1150shows a magnified view of the interface between the impeller 114 and thediffuser portion 310. When the impeller 114 and the diffuser portion 310are cold (e.g., at startup, as illustrated by solid lines), there is asmall space between the impeller 114 and the diffuser portion 310.Moreover, the impeller 114 and the diffuser portion 310 are aligned suchthat compressed air exiting the impeller radially is transferred to thediffuser. As the system heats up (e.g., during operation, as illustratedby the dashed lines), the hot impeller 1114 may expand radially andshifts forward slightly. Due the support structure of the aero component300 and the load path 1136, the hot diffuser 1310 also expands radiallyand shifts forward slightly. The forward shift may be kept below athreshold. Accordingly, the spacing between the hot impeller 1114 andthe hot diffuser 1310 remains approximately the same as the spacingbetween the cold impeller 114 and the cold diffuser portion 310. In anaspect, the critical dimension between the impeller 114 and the diffuserportion 310 is maintained within 10% when the temperature of the systemincreases by at least 200 degrees Fahrenheit. Moreover, the hot diffuser1310 maintains a radial alignment. For example, unlike the hot diffuser154 the hot diffuser 1310 maintains the same orientation with respect tothe impeller 114. Accordingly, the interface between the impeller 114and the diffuser portion 310 maintains transfer efficiency as the systemheats up.

The monolithic superstructure 200 may be manufactured using an additivemanufacturing (AM) process. AM encompasses various manufacturing andprototyping techniques known under a variety of names, includingfreeform fabrication, 3D printing, rapid prototyping/tooling, etc. AMtechniques are capable of fabricating complex components from a widevariety of materials. Generally, a freestanding object can be fabricatedfrom a computer aided design (CAD) model. A particular type of AMprocess, direct metal laser melting (DMLM), uses an energy beam, forexample, an electron beam or electromagnetic radiation such as a laserbeam, to sinter or melt a powder material, creating a solidthree-dimensional object in which particles of the powder material arebonded together. AM may be particularly applicable for manufacturing,for example, the monolithic superstructure 200, which includes multipleconcentric and coaxial subcomponents. In an aspect, the monolithicsuperstructure 200 may be fabricated in a layer-by-layer manner alongthe longitudinal axis. The AM process may fabricate the monolithicsuperstructure as an integrated structure. Various supports may be usedto position portions of the monolithic superstructure during a buildprocess. The supports and any unfused powder may be removed from themonolithic superstructure 200 upon completion. Further, additionalcomponents such as replaceable bearings, fuel lines, instrumentation,etc. may be mounted to the superstructure. In an aspect, one or more ofthe components described above may be replaced with a similar componentmounted to a fixture integrated into the superstructure.

In an aspect, the monolithic and integrated design of the monolithicsuperstructure 200 integrates services and features as a singlecomponent. Design optimization may be performed for the integrateddesign rather than at a sub-component level. For example, lead paths,case and pressure vessel properties, aerodynamics and relatedperformance, weight, and cost can be optimized as a holistic sub-systemdesign. Additionally, the integrated design allows features (e.g.,integrated deswirler tubes 330 and annular aero component support 370)that could not be practically assembled as separate components. Theintegrated structure also reduces assembly risks related to thefunctional and physical attributes of separate components. Accordingly,the integrated structure allows for manufacture of a sub-system in apredictable and repeatable manner.

This written description uses examples to disclose the invention,including the preferred embodiments, and also to enable any personskilled in the art to practice the invention, including making and usingany devices or systems and performing any incorporated methods. Thepatentable scope of the invention is defined by the claims, and mayinclude other examples that occur to those skilled in the art. Suchother examples are intended to be within the scope of the claims if theyhave structural elements that do not differ from the literal language ofthe claims, or if they include equivalent structural elements withinsubstantial differences from the literal language of the claims.Aspects from the various embodiments described, as well as other knownequivalents for each such aspect, can be mixed and matched by one ofordinary skill in the art to construct additional embodiments andtechniques in accordance with principles of this application.

The invention claimed is:
 1. A monolithic superstructure of a gasturbine engine comprising: an outer case including a longitudinallyproximal diffuser case portion, at least one mounting flange formounting to a compressor case, and a longitudinally distal combustorcase portion; a sump housing connected to the outer case via a conicalportion; and an aero component connected to the outer case, the aerocomponent including a diffuser portion and a deswirler portioncomprising a plurality of conjoined tubes extending from a radial end ofthe diffuser portion to an interior of the combustor case portion, thediffuser case portion not directly connected to the diffuser portion,wherein; the aero component connects the conical portion to the outercase to form a load path extending from the sump housing to the outercase via the conical portion and mounting tabs, the mounting tabsdownstream of the aero component; and the at least one mounting flangeis disposed upstream of the longitudinally proximal diffuser caseportion.
 2. The monolithic superstructure of claim 1, further comprisingan annular aero portion support, the annular aero portion supportdividing an interior of the outer case into a forward region and an aftregion, and wherein the plurality of conjoined tubes extend from theforward region to the aft region.
 3. The monolithic superstructure ofclaim 1, wherein the diffuser portion is spaced from an impeller.
 4. Themonolithic superstructure of claim 3, wherein the aero component expandsradially as a temperature of the aero component increases.
 5. Themonolithic superstructure of claim 4, wherein a spacing between thediffuser portion and the impeller is maintained within 10% when thetemperature of the aero component increases by at least 200 degreesFahrenheit.
 6. The monolithic superstructure of claim 3, wherein thedeswirler portion further comprises a compressor impeller back wallswirl plate axially aft of the impeller.
 7. The monolithicsuperstructure of claim 1, wherein the sump housing extends from anaxially aft surface of the aero component, the sump housing comprisingan embedded turbine cooling passage.
 8. The monolithic superstructure ofclaim 7, wherein the plurality of conjoined tubes form a portion of anouter wall of the sump housing, the plurality of conjoined tubesincluding a plurality of air extraction ports providing fluidcommunication between the plurality of conjoined tubes and an interiorof the sump housing.
 9. The monolithic superstructure of claim 8,further comprising a turbine cooling accelerator located at an aft endof the sump housing.
 10. The monolithic superstructure of claim 7,further comprising at least one bearing extending radially inward fromthe sump housing.
 11. The monolithic superstructure of claim 2, whereinthe outer case further comprises a turbine cooling passage extendingfrom the forward region to an aft end of the outer case.
 12. Themonolithic superstructure of claim 6, further comprising an annularimpeller back wall stiffener having a triangular cross-section extendingfrom an axially aft surface of the impeller back wall swirl plate. 13.The monolithic superstructure of claim 2, wherein the annular aeroportion support limits thermal coupling between the outer case and theaero component.
 14. The monolithic superstructure of claim 2, whereinthe sump housing includes a bearing support for mounting bearings tosupport a shaft of the gas turbine engine.
 15. The monolithicsuperstructure of claim 2, wherein the conical portion supports the aerocomponent.
 16. A method of supporting loads in a gas turbine engine, thegas turbine engine comprising a monolithic superstructure comprising: anouter case including a longitudinally proximal diffuser case portion, atleast one mounting flange for mounting to a compressor case, and alongitudinally distal combustor case portion; a sump housing connectedto the outer case via a conical portion; and an aero component connectedto the outer case, the aero component including a diffuser portion and adeswirler portion comprising a plurality of conjoined tubes extendingfrom a radial end of the diffuser portion to an interior of thecombustor case portion, the diffuser case portion not directly connectedto the diffuser portion, wherein; the aero component connects theconical portion to the outer case to form a load path extending from thesump housing to the outer case via the conical portion and mountingtabs, the mounting tabs downstream of the aero component; and the atleast one mounting flange is disposed upstream of the longitudinallyproximal diffuser case portion; and the method comprising: transferringa load from a rotating shaft to a bearing portion of the sump housingvia contact between the rotating shaft and the bearing portion;transferring the load from the bearing portion via the conical portionof the sump housing to the aero component; transferring the load fromthe aero component to an annular aero component support connected to theplurality of conjoined tubes; transferring the load from the annularaero component support to the mounting tabs; and transferring the loadfrom the mounting tabs to a frame supporting the gas turbine engine.